Variable area turbine vane row assembly

Patent metadata

Field	Value
Publication number	US-10519796-B2
Application number	US-201415022227-A
Country	US
Kind code	B2
Filing date	Sep 16, 2014
Priority date	Sep 16, 2013
Publication date	Dec 31, 2019
Grant date	Dec 31, 2019

Abstract

The present disclosure relates generally to a variable area turbine vane row assembly. In an embodiment, the variable area turbine vane row assembly includes rotatable vanes that are circumferentially biased and/or axially biased with respect to adjacent fixed vanes. In another embodiment, the variable area turbine vane row assembly includes multiple rotatable vanes positioned between adjacent fixed vanes, which may optionally be circumferentially biased and/or axially biased with respect to each other as well as to the adjacent fixed vanes.

First claim

What is claimed:

1. A variable area turbine vane row assembly, comprising:
a first fixed vane located in a first circumferential vane row organized circumferentially around a rotational axis of a gas turbine engine;
a second fixed vane located in the first circumferential vane row, the second fixed vane being proximate the first fixed vane; and
a plurality of rotatable vanes located in the first circumferential vane row, the plurality of rotatable vanes being positioned between the first fixed vane and the second fixed vane;
wherein no other fixed vanes are positioned between the first fixed vane and the second fixed vane within the first circumferential vane row, and
wherein the first fixed vane, the second fixed vane, and the plurality of rotatable vanes form a segment of the first circumferential vane row.

2. The variable area turbine vane row assembly of claim 1 , wherein the plurality of rotatable vanes comprises three rotatable vanes.

3. The variable area turbine vane row assembly of claim 1 , wherein the plurality of rotatable vanes comprises a first rotatable vane and a second rotatable vane.

4. The variable area turbine vane row assembly of claim 3 , wherein the first rotatable vane is asymmetrically positioned within the first circumferential van row between the first fixed vane and the second rotatable vane in at least one of a circumferential direction as measured circumferentially around the rotational axis of the gas turbine engine and an axial direction as measured axially along the rotational axis of the gas turbine engine.

5. The variable area turbine vane row assembly of claim 4 , wherein the first rotatable vane is circumferentially biased toward the first fixed vane in the circumferential direction as measured circumferentially around the rotational axis of the gas turbine engine within the first circumferential vane row.

6. The variable area turbine vane row assembly of claim 5 , wherein the first rotatable vane is circumferentially biased toward a suction side of the first fixed vane in the circumferential direction as measured circumferentially around the rotational axis of the gas turbine engine within the first circumferential vane row.

7. The variable area turbine vane row assembly of claim 5 , wherein the first rotatable vane is circumferentially biased toward a pressure side of the first fixed vane in the circumferential direction as measured circumferentially around the rotational axis of the gas turbine engine within the first circumferential vane row.

8. The variable area turbine vane row assembly of claim 3 , wherein the first rotatable vane is axially biased in aft design direction with respect to the first fixed vane and the second fixed vane in the axial direction as measured axially along the rotational axis of the gas turbine engine within the first circumferential vane row.

9. The variable area turbine vane row assembly of claim 3 , wherein the first rotatable vane is axially biased in a forward design direction with respect to the first fixed vane and the second fixed vane in the axial direction as measured axially along the rotational axis of the gas turbine engine within the first circumferential vane row.

10. The variable area turbine vane row assembly of claim 3 , wherein the first rotatable vane is both circumferentially biased toward the first fixed vane in the circumferential direction as measured circumferentially around the rotational axis of the gas turbine engine within the first circumferential vane row and axially biased in a forward design direction with respect to the first fixed vane and the second fixed vane in the axial direction as measured axially along the rotational axis of the gas turbine engine within the first circumferential vane row.

11. The variable area turbine vane row assembly of claim 3 , wherein the first rotatable vane is both circumferentially biased toward the first fixed vane in the circumferential direction as measured circumferentially around the rotational axis of the gas turbine engine within the first circumferential vane row and axially biased in an aft design direction with respect to the first fixed vane and the second fixed vane in the axial direction as measured axially along the rotational axis of the gas turbine engine within the first circumferential vane row.

Assignees

• United Technologies Corp
• Grover Eric A

Inventors

• Grover Eric A

Classifications

• F01D17/162 Primary

  for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line (F01D17/167 takes precedence) · CPC title

• F05D2240/124

  related to the suction side of a stator vane · CPC title

• F01D9/041

  using blades (F01D5/148 takes precedence) · CPC title

• F05D2250/73

  asymmetric · CPC title

• F05D2220/32

  in gas turbines · CPC title